EP0041878A2 - Fuel injection device for a gas turbine - Google Patents

Fuel injection device for a gas turbine Download PDF

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Publication number
EP0041878A2
EP0041878A2 EP81400797A EP81400797A EP0041878A2 EP 0041878 A2 EP0041878 A2 EP 0041878A2 EP 81400797 A EP81400797 A EP 81400797A EP 81400797 A EP81400797 A EP 81400797A EP 0041878 A2 EP0041878 A2 EP 0041878A2
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EP
European Patent Office
Prior art keywords
injection
fuel
assembly according
orifices
injection assembly
Prior art date
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Granted
Application number
EP81400797A
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German (de)
French (fr)
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EP0041878B1 (en
EP0041878A3 (en
Inventor
Bruno Deroide
Philippe Marc Denis Gastebois
Alain Jacques Gérard Jacquet
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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Publication of EP0041878A2 publication Critical patent/EP0041878A2/en
Publication of EP0041878A3 publication Critical patent/EP0041878A3/en
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Publication of EP0041878B1 publication Critical patent/EP0041878B1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/12—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour characterised by the shape or arrangement of the outlets from the nozzle

Definitions

  • the invention relates to a fuel injection assembly for a turbojet combustion chamber, comprising a swirl vane for combustion air and a fuel injector.
  • the devices for injecting fuel into the combustion chambers of a jet engine are generally designed so that they produce a forceful shearing effect on the flow of fuel. This shearing effect is the result of the combined action of air flow, passing through two swirl blades, between which the fuel is introduced.
  • the injector is in the form of an annular nozzle, surrounded by a duct for the passage of a first air flow, the central part of which channels a second air flow.
  • the two air flows as well as the fuel pass through vortex blades and interpenetrate at their exit to form an air fuel mixture in which the latter is finely divided.
  • the injection assembly according to the invention always uses spraying by shearing of the fuel by an air flow, but uses a simplified device.
  • the fuel injection assembly for a turbojet combustion chamber in which the fuel droplets are fractionated by a swirling air flow is remarkable in that it comprises a unique swirl vane.
  • a unique swirl vane for the rotation of the air flow, constituted by a cylindrical centripetal vane whose trailing edges of the vanes define a volume / connected downstream to a cylindro-conical bowl by which the assembly is fixed to the chamber and upstream to the fuel droplet injection device.
  • the fuel droplet injection device consists of a hollow body, the bottom of which has a fuel inlet and the cap of the injection orifices projection for fuel passage.
  • the injection assembly is fixed to the bottom of a combustion chamber and is bathed in a flow of air from the compressors.
  • the assembly comprises a device for injecting fuel droplets 1, onto which is fixed a centripetal blading or "swirler" 2 defining at its center a cylindrical volume extended by a tubular conduit 3.
  • the tubular conduit is connected downstream to a conical bowl 4.
  • the air coming from the compressors passes through the vane 2 and takes a vortex movement as a result of the inclination of the blades.
  • the change in orientation of the air flow entering through the blading is facilitated by the shape of the cap 8 of the injection device 1, projecting into the cylindrical volume.
  • the fuel (arrows in broken lines) sprayed by the nozzles or injection orifices 5 in a direction substantially parallel to the axis of the device, comes to cut off the swirling air flow.
  • the droplets finely pulverized by the meeting of air and fuel flows, mix intimately with the combustion air and form a homogeneous mixture.
  • the injection device 1 consists of a hollow cylindrical body having, according to the embodiment, a frustoconical bottom 6 at the center of which is fixed the tube 7 for the fuel inlet.
  • the cap 8 of the cylindrical body has an approximate / conical shape and carries near its periphery injection orifices 5 distributed in at least one concentric circle. The orifices are arranged so as to be between the trailing edges 9 of the swirl vanes.
  • the cap 8 of the cylindrical body (Fig. 2) has a conical central portion 10 which is connected by a rounded large radius 11 to a flat annular peripheral portion 12 on which are provided the injection orifices 5.
  • the cap 8 which closes the upstream end of the cylindrical volume 3, is not likely to present carbon dep8ts because they are swept by the air of the centripetal vane, and cannot heat up because it is cooled by the penetrating fuel in the cylindrical body.
  • a conical skirt 16 is provided upstream.
  • the injection orifices 5 are distributed on a circle concentric with the axis of the assembly including the diameter is between 0.7 and 0.9 times the diameter of the circle determined by the trailing edges 9 of the swirl vanes 2.
  • the injection orifices 5 project from the surface of the cap 8. According to embodiments, the orifices open at the top of blocks welded to the cap (Fig. 3A), or at the end of the axis tubes parallel to the axis of the assembly (Fig. 3B).
  • the remoteness of the injection orifices 5 from the surface of the cap 8 has two advantages: avoiding the dripping of fuel on the cap, obtaining a flow of fuel perpendicular to the air flow at the level of the injection allowing the obtaining of '' a homogeneous mixture of fine droplets.
  • the number of injection orifices 5 may be different from the number of intervals between the blades, however it must at least be equal to the integer closest to one third of the diameter expressed in mm of the circle on which the orifices are located.
  • the cylindrical volume 3 is extended by a frustoconical bowl 4 which carries on its downstream edge a flange 13.
  • This flange cooperates with a fixing device provided on the chamber and comprising means for allowing the movements of the flange both in the axial direction as in the radial direction.
  • a cylindrical skirt 14 coaxial with the axis of the assembly is fixed near the edge carrying the flange 13. The skirt 14 facilitates the entoncession of the air coming from the compressors towards the injection assembly and forces it to penetrate by one or more rows of holes 15 in the bowl 4 where it mixes with the air fuel flow and allows better combustion at low speeds.
  • the operating mode of the assembly is conventional in the type of aerodynamic injection.
  • the air set in rotation creates a central depression in the axis of the injector which favors a return current in the upstream part of the combustion chamber, and the conditions for good combustion are thus met.
  • This embodiment adapted to machines of small dimensions with the technological simplification obtained has great reliability and an attractive cost.
  • the embodiment described provides a set of performances in terms of ignition, stability, thermal resistance and pollution.

Abstract

1. Fuel injection assembly for a combustion chamber of a turbo-jet engine in which a single array of swirl blading (2) for rotationally impelling a flow of air, is constituted by a centripetal blading array discharging into a cylindrical space disposed downstream of an injection device so as to break up the droplets of fuel by the swirling air flow, characterized in this that the said cylindrical space is extended by a tubular duct (3) connected downstream to a conical bowl (4) and in this the said injection device is formed by a hollow cylindrical body of which the base (6) comprises a fuel inlet (7) and the hood (8) of the infection orifices (5) projects for the passage of the fuel so that the transverse outlet plane of the orifices (5) is very close to the plane of the upstream end of the blading array (2).

Description

L'invention concerne un ensemble d'injection de carburant pour une chambre de combustion de turboréacteur, comprenant un aubage de tourbillonnement pour l'air de combustion et un injecteur de carburant.The invention relates to a fuel injection assembly for a turbojet combustion chamber, comprising a swirl vane for combustion air and a fuel injector.

Les-dispositifs d'injection de carburant dans les chambres de combustion de moteur à réaction sont généralement conçus de manière qu'ils produisent un effet de cisaillement énergique sur le flux de carburant. Cet effet de cisaillement est le résultat de l'action combinée de flux d'air, passant par deux aubages de tourbillonnement, entre lesquels on introduit le carburant.The devices for injecting fuel into the combustion chambers of a jet engine are generally designed so that they produce a forceful shearing effect on the flow of fuel. This shearing effect is the result of the combined action of air flow, passing through two swirl blades, between which the fuel is introduced.

L'amenée de carburant est faite de différentes manières. C'est ainsi que dans le brevet français 2.235.274, l'injecteur se présente sous la forme d'une buse annulaire, entourée d'un conduit pour le passage d'un premier flux d'air, dont la partie centrale canalise un second flux d'air. Les deux flux d'air ainsi que le carburant passent dans des aubages de tourbillonnement et s'interpénètrent à leur sortie pour former un mélange air carburant dans lequel ce dernier est finement divisé.Fuel delivery is done in different ways. Thus, in French patent 2,235,274, the injector is in the form of an annular nozzle, surrounded by a duct for the passage of a first air flow, the central part of which channels a second air flow. The two air flows as well as the fuel pass through vortex blades and interpenetrate at their exit to form an air fuel mixture in which the latter is finely divided.

Dans le brevet français 2.206.796, le carburant est envoyé dans des canaux débouchant tangentiellement dans un espace annulaire dont l'ouverture délivre un anneau de carburant pulvérisé entre deux flux d'air tourbillonnaires.In French patent 2,206,796, the fuel is sent through channels tangentially opening into an annular space, the opening of which delivers a ring of sprayed fuel between two vortex air flows.

Dans le brevet des Etats Unis d'Amérique 3.703.259, le carburant est introduit par des ouvertures radiales ou axiales dans un premier flux d'air tourbillonnant. Ce flux rencontre un deuxième flux d'air tourbillonnant en sens inverse et provoque, dans la zone de rencontre, un flux d'air turbulent qui divise finement les gouttelettes de carburant transportées par le premier flux.In United States patent 3,703,259, the fuel is introduced through radial or axial openings into a first swirling air flow. This flow meets a second flow of air swirling in the opposite direction and causes, in the meeting zone, a flow turbulent air which finely divides the fuel droplets transported by the first flow.

Il ressort des documents analysés ainsi que de l'opinion généralement admise chez les motoristes, que l'obtention d'une bonne pulvérisation et d'un bon mélange du carburant dans l'air de combustion passe nécessairement par l'utilisation d'ensembles d'injection comportant au moins deux aubages de tourbillonnement par lesquels passe l'air de combustion, le carburant étant injecté directement entre les deux flux ou étant transporté par un des flux.It appears from the documents analyzed and from the opinion generally accepted among engine manufacturers, that obtaining a good spraying and a good mixture of fuel in the combustion air necessarily involves the use of sets of injection comprising at least two swirl blades through which the combustion air passes, the fuel being injected directly between the two streams or being transported by one of the streams.

Les avantages de ces techniques d'injection aérodynamiques sont largement connus, mais l'application de ce type d'injecteur aux machines de petites dimensions devient impraticable par suite des contraintes dimensionnelles de la réalisation et des nécessités de réduction de l'encombrement.The advantages of these aerodynamic injection techniques are widely known, but the application of this type of injector to machines of small dimensions becomes impracticable due to the dimensional constraints of the production and the need to reduce the size.

L'ensemble d'injection selon l'invention utilise toujours la pulvérisation par cisaillement du carburant par un écoulement d'air, mais met en oeuvre un dispositif simplifié.The injection assembly according to the invention always uses spraying by shearing of the fuel by an air flow, but uses a simplified device.

L'ensemble d'injection de carburant, selon 1-linvention, pour une chambre de combustion de turboréacteur dans lequel les gouttelettes de carburant sont fractionnées par un flux d'air tourbillonnant est remarquable en ce qu'il comporte un aubage de tourbillonnement unique, pour la mise en rotation du flux d'air, constitué par un aubage centripète cylindrique dont les bords de fuite des aubes délimitent un volume/rac- cordé en aval à un bol cylindro-conique par lequel l'ensemble est fixé à la chambre de combustion et en amont au dispositif d'injection des gouttelettes de carburant. Le dispositif d'injection des gouttelettes de carburant est constitué d'un corps creux dont le fond comporte une arrivée de carburant et le chapeau des orifices d'injection en saillie pour le passage du carburant.The fuel injection assembly, according to the invention, for a turbojet combustion chamber in which the fuel droplets are fractionated by a swirling air flow is remarkable in that it comprises a unique swirl vane. , for the rotation of the air flow, constituted by a cylindrical centripetal vane whose trailing edges of the vanes define a volume / connected downstream to a cylindro-conical bowl by which the assembly is fixed to the chamber and upstream to the fuel droplet injection device. The fuel droplet injection device consists of a hollow body, the bottom of which has a fuel inlet and the cap of the injection orifices projection for fuel passage.

Les explications et figures données ci-après à titre d'exemple permettront de comprendre comment l'invention peut être réalisée.

  • La figure 1 est une vue en perspective, partiellement arrachée d'un ensemble d'injection selon l'invention.
  • La figure 2 montre une coupe de l'ensemble selon la figure 1.
  • Les figures 3A et 3B sont une vue selon III-III de la figure 2 montrant deux formes de réalisation des orifices d'injection.
  • La figure 1 montre une vue en perspective et partiellement arrachée d'un ensemble d'injection selon l'invention.
The explanations and figures given below by way of example will make it possible to understand how the invention can be implemented.
  • Figure 1 is a perspective view, partially broken away of an injection assembly according to the invention.
  • Figure 2 shows a section of the assembly according to Figure 1.
  • Figures 3A and 3B are a view along III-III of Figure 2 showing two embodiments of the injection orifices.
  • Figure 1 shows a perspective view and partially broken away of an injection assembly according to the invention.

L'ensemble d'injection est fixé sur le fond d'une chambre de combustion et se trouve baigné par un flux d'air provenant des compresseurs.The injection assembly is fixed to the bottom of a combustion chamber and is bathed in a flow of air from the compressors.

L'ensemble comprend un dispositif d'injection 1 de gouttelettes de carburant, sur lequel est fixé un aubage ou "swirler" centripète 2 définissant en son centre un volume cylindrique prolongé par un conduit tubulaire 3. Le conduit tubulaire est raccordé en aval à un bol conique 4.The assembly comprises a device for injecting fuel droplets 1, onto which is fixed a centripetal blading or "swirler" 2 defining at its center a cylindrical volume extended by a tubular conduit 3. The tubular conduit is connected downstream to a conical bowl 4.

L'air provenant des compresseurs (flèches en trait plein) passe dans l'aubage 2 et prend un mouvement tourbillonnaire par suite de l'inclinaison des aubes. Le changement d'orientation du flux d'air pénétrant par l'aubage est facilité par la forme du chapeau 8 du dispositif d'injection 1,faisant saillie dans le volume cylindrique.The air coming from the compressors (arrows in solid line) passes through the vane 2 and takes a vortex movement as a result of the inclination of the blades. The change in orientation of the air flow entering through the blading is facilitated by the shape of the cap 8 of the injection device 1, projecting into the cylindrical volume.

Le carburant, (flèches en trait interrompu) pulvérisé par les buses ou orifices d'injection 5 dans une direction sensiblement parallèle à l'axe du dispositif, vient couper le flux d'air tourbillonnant. Les gouttelettes, finement pulvérisées par la rencontre des flux d'air et de carburant, se mélangent intimement à l'air de combustion et forment un mélange homogène.The fuel (arrows in broken lines) sprayed by the nozzles or injection orifices 5 in a direction substantially parallel to the axis of the device, comes to cut off the swirling air flow. The droplets, finely pulverized by the meeting of air and fuel flows, mix intimately with the combustion air and form a homogeneous mixture.

Le dispositif d'injection 1 est constitué d'un corps cylindrique creux présentant selon l'exemple de réalisation un fond 6 tronconique au centre duquel est fixé le tube 7 d'arrivée de carburant. Le chapeau 8 du corps cylindrique a une forme approximative/conique et porte près de sa périphérie des orifices d'injection 5 répartis selon au moins un cercle concentrique. Les orifices sont disposés de manière à se trouver entre les bords de fuite 9 des aubes de tourbillonnement. De préférence le chapeau 8 du corps cylindrique (Fig. 2) présente une portion centrale conique 10 qui se raccorde par un arrondi à grand rayon 11 à une portion périphérique annulaire plane 12 sur laquelle sont prévues les orifices d'injection 5. Le chapeau 8, qui ferme l'extrémité amont du volume cylindrique 3, ne risque pas de présenter des dép8ts de carbone car ils sont balayés par l'air de l'aubage centripète, et ne peut pas s'échauffer car il est refroidi par le carburant pénétrant dans le corps cylindrique. Afin de faciliter le centrage du corps d'injection, on prévoit, en amont, une jupe conique 16. Selon une forme préférée de réalisation, les orifices d'injection 5 sont répartis sur un cercle concentrique à l'axe de l'ensemble dont le diamètre est compris entre 0,7 et 0,9 fois le diamètre du cercle déterminé par les bords de fuite 9 des aubes de tourbillonnement 2.The injection device 1 consists of a hollow cylindrical body having, according to the embodiment, a frustoconical bottom 6 at the center of which is fixed the tube 7 for the fuel inlet. The cap 8 of the cylindrical body has an approximate / conical shape and carries near its periphery injection orifices 5 distributed in at least one concentric circle. The orifices are arranged so as to be between the trailing edges 9 of the swirl vanes. Preferably the cap 8 of the cylindrical body (Fig. 2) has a conical central portion 10 which is connected by a rounded large radius 11 to a flat annular peripheral portion 12 on which are provided the injection orifices 5. The cap 8 , which closes the upstream end of the cylindrical volume 3, is not likely to present carbon dep8ts because they are swept by the air of the centripetal vane, and cannot heat up because it is cooled by the penetrating fuel in the cylindrical body. In order to facilitate centering of the injection body, a conical skirt 16 is provided upstream. According to a preferred embodiment, the injection orifices 5 are distributed on a circle concentric with the axis of the assembly including the diameter is between 0.7 and 0.9 times the diameter of the circle determined by the trailing edges 9 of the swirl vanes 2.

Les orifices d'injection 5 sont en saillie par rapport à la surface du chapeau 8. Selon des formes de réalisation, les orifices débouchent au sommet de pavés soudés sur le chapeau (Fig. 3A), ou à l'extrémité du tubes d'axes parallèles à l'axe de l'ensemble (Fig. 3B). L'éloignement des orifices d'injection 5 de la surface du chapeau 8 présente deux avantages : éviter le ruissellement de carburant sur le chapeau, obtenir un écoulement de carburant perpendiculaire au flux d'air au niveau de l'injection permettant l'obtention d'un mélange homogène de fines gouttelettes.The injection orifices 5 project from the surface of the cap 8. According to embodiments, the orifices open at the top of blocks welded to the cap (Fig. 3A), or at the end of the axis tubes parallel to the axis of the assembly (Fig. 3B). The remoteness of the injection orifices 5 from the surface of the cap 8 has two advantages: avoiding the dripping of fuel on the cap, obtaining a flow of fuel perpendicular to the air flow at the level of the injection allowing the obtaining of '' a homogeneous mixture of fine droplets.

Le nombre des orifices d'injection 5 peut être différent du nombre d'intervalles entre les aubes, toutefois il doit au moins être égal à l'entier le plus proche du tiers du diamètre exprimé en mm du cercle sur lequel sont situés les orifices.The number of injection orifices 5 may be different from the number of intervals between the blades, however it must at least be equal to the integer closest to one third of the diameter expressed in mm of the circle on which the orifices are located.

Le volume cylindrique 3 est prolongé par un bol tronconique 4 qui porte sur son bord aval une bride 13. Cette bride coopère avec un dispositif de fixation prévu sur la chambre et comportant des moyens pour permettre les déplacements de la bride tant dans le sens axial que dans le sens radial. Une jupe cylindrique 14 coaxiale à l'axe de l'ensemble est fixée près du bord portant la bride 13. La jupe 14 facilite l'entonnement de l'air provenant des compresseurs vers l'ensemble d'injection et l'oblige à pénétrer par une ou plusieurs rangées de trous 15 dans le bol 4 où il se mélange au flux air carburant et permet une meilleure combustion aux bas régimes.The cylindrical volume 3 is extended by a frustoconical bowl 4 which carries on its downstream edge a flange 13. This flange cooperates with a fixing device provided on the chamber and comprising means for allowing the movements of the flange both in the axial direction as in the radial direction. A cylindrical skirt 14 coaxial with the axis of the assembly is fixed near the edge carrying the flange 13. The skirt 14 facilitates the entonnement of the air coming from the compressors towards the injection assembly and forces it to penetrate by one or more rows of holes 15 in the bowl 4 where it mixes with the air fuel flow and allows better combustion at low speeds.

Le mode de fonctionnement de l'ensemble est classique dans le type d'injection aérodynamique. L'air mis en rotation crée une dépression centrale dans l'axe de l'injecteur ce qui favorise un courant de retour dans la partie amont de la chambre de combustion, et les conditions d'une bonne combustion sont ainsi réunies.The operating mode of the assembly is conventional in the type of aerodynamic injection. The air set in rotation creates a central depression in the axis of the injector which favors a return current in the upstream part of the combustion chamber, and the conditions for good combustion are thus met.

Cette réalisation adaptée aux machines de petites dimensions avec la simplification technologique obtenue présente une grande fiabilité et un coût intéressant.This embodiment adapted to machines of small dimensions with the technological simplification obtained has great reliability and an attractive cost.

Le mode de réalisation décrit assure un ensemble de performances au niveau de l'allumage, de la stabilité, de la tenue thermique et de la pollution.The embodiment described provides a set of performances in terms of ignition, stability, thermal resistance and pollution.

Claims (9)

1. Ensemble d'injection de carburant pour une chambre de combustion de turboréacteur dans lequel les gouttelettes de carburant sont fractionnées par un flux d'air tourbillonnant, caractérisé en ce 'qu'il comporte un aubage de tourbillonnement (2) unique, pour la mise en rotation du flux d'air, constitué par un aubage centripète débouchant dans un volume cylindrique (3) disposé en aval du dispositif d'injection des gouttelettes de carburant, ledit volume étant prolongé par un conduit tubulaire raccordé en aval à un bol conique (4).1. Fuel injection assembly for a turbojet combustion chamber wherein the fuel droplets are broken by a swirling airflow, characterized in that 'it comprises a swirl vane (2) unique for the rotation of the air flow, consisting of a centripetal blade opening into a cylindrical volume (3) disposed downstream of the fuel droplet injection device, said volume being extended by a tubular conduit connected downstream to a conical bowl (4). 2. Ensemble d'injection selon la revendication 1, caractérisé en ce que le dispositif d'injection des gouttelettes de carburant est formé d'un corps cylindrique creux dont le fond (6) comporte une arrivée de carburant (7) et le chapeau (8) des orifices d'injection (5) en saillie pour le passage du carburant.2. Injection assembly according to claim 1, characterized in that the fuel droplet injection device is formed by a hollow cylindrical body whose bottom (6) has a fuel inlet (7) and the cap ( 8) projecting injection orifices (5) for the passage of fuel. 3. Ensemble d'injection selon la revendication 2, caractérisé en ce que les orifices d'injection (5) sont constitués par des tubes parallèles à l'axe de l'ensemble d'injection.3. Injection assembly according to claim 2, characterized in that the injection orifices (5) are constituted by tubes parallel to the axis of the injection assembly. 4. Ensemble d'injection selon l'une des revendications précédentes, caractérisé en ce que le chapeau (8) du corps cylindrique creux présente au centre une forme approximativement conique (10) dont la convexité est tournée vers la chambre de combustion se raccordant par un arrondi à grand rayon (11) à une portion périphérique annulaire plane (12).4. Injection assembly according to one of the preceding claims, characterized in that the cap (8) of the hollow cylindrical body has in the center an approximately conical shape (10) whose convexity is turned towards the combustion chamber connected by a rounded large radius (11) to a flat annular peripheral portion (12). 5. Ensemble d'injection selon l'une des revendications précédentes, caractérisé en ce que chaque orifice d'injection (5) est situé entre les bords de fuite (9) de deux aubes voisines.5. Injection assembly according to one of the preceding claims, characterized in that each injection orifice (5) is located between the trailing edges (9) of two neighboring blades. 6. Ensemble d'injection selon la revendication 5, caractérisé en ce que les orifices d'injection (5) sont situés sur un cercle concentrique à l'axe de l'ensemble dont le diamètre est compris entre 0,7 et 0,9 fois le diamètre du cercle déterminé par les bords de fuite (9) des aubes de tourbillonnement.6. Injection assembly according to claim 5, characterized in that the injection orifices (5) are located on a circle concentric with the axis of the assembly whose diameter is between 0.7 and 0.9 times the diameter of the circle determined by the trailing edges (9) of the swirl vanes. 7. Ensemble d'injection selon la revendication 6, caractérisé en ce que le nombre minimum d'orifices d'injection (5) est égal à l'entier le plus proche du tiers du diamètre exprimé en mm du cercle sur lequel sont situés les orifices.7. Injection assembly according to claim 6, characterized in that the minimum number of injection orifices (5) is equal to the integer closest to one third of the diameter expressed in mm of the circle on which the orifices. 8. Ensemble d'injection selon l'une des revendications précédentes, caractérisé en ce que le bol conique (4) porte, près de son bord, des trous (15) disposés selon une ou plusieurs rangées.8. Injection assembly according to one of the preceding claims, characterized in that the conical bowl (4) carries, near its edge, holes (15) arranged in one or more rows. 9. Ensemble d'injection selon la revendication 6, caractérisé en ce que le bol conique (4) porte une jupe cylindrique (14) coaxiale à l'axe de l'ensemble, fixée sur le bord du bol conique (4) de manière à canaliser le flux d'air vers les trous (15).9. Injection assembly according to claim 6, characterized in that the conical bowl (4) carries a cylindrical skirt (14) coaxial with the axis of the assembly, fixed on the edge of the conical bowl (4) so to channel the air flow towards the holes (15).
EP19810400797 1980-06-06 1981-05-21 Fuel injection device for a gas turbine Expired EP0041878B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8012558A FR2484020A1 (en) 1980-06-06 1980-06-06 FUEL INJECTION ASSEMBLY FOR TURBOREACTOR CHAMBER
FR8012558 1980-06-06

Publications (3)

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EP0041878A2 true EP0041878A2 (en) 1981-12-16
EP0041878A3 EP0041878A3 (en) 1982-09-22
EP0041878B1 EP0041878B1 (en) 1984-08-01

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ID=9242761

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19810400797 Expired EP0041878B1 (en) 1980-06-06 1981-05-21 Fuel injection device for a gas turbine

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EP (1) EP0041878B1 (en)
DE (1) DE3165211D1 (en)
FR (1) FR2484020A1 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0548908A2 (en) * 1991-12-24 1993-06-30 Kabushiki Kaisha Toshiba Fuel jetting nozzle assembly for use in gas turbine combustor
EP2481982A1 (en) * 2011-01-26 2012-08-01 United Technologies Corporation Mixer assembly for a gas turbine engine
CN104776430A (en) * 2015-04-15 2015-07-15 陈民 Novel high-energy-saving environment-friendly liquid combustor
US9920932B2 (en) 2011-01-26 2018-03-20 United Technologies Corporation Mixer assembly for a gas turbine engine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1698258A (en) * 1926-07-16 1929-01-08 Adolf F Haffenreffer Method of combustion
FR1094871A (en) * 1959-01-22 1955-05-25 Thomson Houston Comp Francaise Improvements to injected fuel combustion devices
FR1462091A (en) * 1965-01-04 1966-12-09 Carrier Corp Flame stabilization
FR2043412A5 (en) * 1969-04-17 1971-02-12 Gen Electric
FR2086476A1 (en) * 1970-04-30 1971-12-31 Gen Electric
FR2300964A1 (en) * 1975-02-12 1976-09-10 Fascione Pietro ALI PROCESS
FR2330871A2 (en) * 1972-11-13 1977-06-03 Snecma Fuel injector for aircraft gas turbine - has swirl vanes to increase fuel flow at low engine speed and to reduce pollution

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1698258A (en) * 1926-07-16 1929-01-08 Adolf F Haffenreffer Method of combustion
FR1094871A (en) * 1959-01-22 1955-05-25 Thomson Houston Comp Francaise Improvements to injected fuel combustion devices
FR1462091A (en) * 1965-01-04 1966-12-09 Carrier Corp Flame stabilization
FR2043412A5 (en) * 1969-04-17 1971-02-12 Gen Electric
FR2086476A1 (en) * 1970-04-30 1971-12-31 Gen Electric
FR2330871A2 (en) * 1972-11-13 1977-06-03 Snecma Fuel injector for aircraft gas turbine - has swirl vanes to increase fuel flow at low engine speed and to reduce pollution
FR2300964A1 (en) * 1975-02-12 1976-09-10 Fascione Pietro ALI PROCESS

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0548908A2 (en) * 1991-12-24 1993-06-30 Kabushiki Kaisha Toshiba Fuel jetting nozzle assembly for use in gas turbine combustor
EP0548908A3 (en) * 1991-12-24 1993-08-25 Kabushiki Kaisha Toshiba Fuel jetting nozzle assembly for use in gas turbine combustor
US5351489A (en) * 1991-12-24 1994-10-04 Kabushiki Kaisha Toshiba Fuel jetting nozzle assembly for use in gas turbine combustor
EP0751345A1 (en) * 1991-12-24 1997-01-02 Kabushiki Kaisha Toshiba Fuel jetting nozzle assembly for use in gas turbine combustor
EP2481982A1 (en) * 2011-01-26 2012-08-01 United Technologies Corporation Mixer assembly for a gas turbine engine
US9920932B2 (en) 2011-01-26 2018-03-20 United Technologies Corporation Mixer assembly for a gas turbine engine
US10718524B2 (en) 2011-01-26 2020-07-21 Raytheon Technologies Corporation Mixer assembly for a gas turbine engine
CN104776430A (en) * 2015-04-15 2015-07-15 陈民 Novel high-energy-saving environment-friendly liquid combustor

Also Published As

Publication number Publication date
FR2484020A1 (en) 1981-12-11
EP0041878B1 (en) 1984-08-01
DE3165211D1 (en) 1984-09-06
FR2484020B1 (en) 1985-05-17
EP0041878A3 (en) 1982-09-22

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